JP6231223B2 - 高圧及び低圧の冷却流体を用いる冷却システムを備えたタービン翼 - Google Patents
高圧及び低圧の冷却流体を用いる冷却システムを備えたタービン翼 Download PDFInfo
- Publication number
- JP6231223B2 JP6231223B2 JP2016555992A JP2016555992A JP6231223B2 JP 6231223 B2 JP6231223 B2 JP 6231223B2 JP 2016555992 A JP2016555992 A JP 2016555992A JP 2016555992 A JP2016555992 A JP 2016555992A JP 6231223 B2 JP6231223 B2 JP 6231223B2
- Authority
- JP
- Japan
- Prior art keywords
- cooling system
- blade
- air
- compressor
- snubber
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
- F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
本発明の開発は、米国エネルギー省の高度タービン開発プログラム、契約番号DE−FC26−05NT42644によって部分的に支援されたものである。従って、米国政府は本発明において一定の権利を有することがある。
本発明は、一般にタービンエンジンに関し、特にガスタービンエンジン内のタービン翼のための周囲冷却空気を用いた冷却流体供給システムに関する。
Claims (7)
- タービン翼(20)であって、
外側壁(34)により形成された概して細長い中空翼(32)であって、前縁(36)と、後縁(38)と、正圧面(40)と、負圧面(42)と、前記翼(20)の第1の端部(46)における根元部(44)と、前記第1の端部(46)とは反対側の第2の端部(50)における先端(48)と、前記概して細長い中空翼(32)の内側に位置している翼冷却システム(10)と、を有する中空翼(32)と、
前記概して細長い中空翼(32)を形成する前記外側壁(34)から、前記概して細長い中空翼(32)を含む翼(20)の列(52)内に位置する隣接するタービン翼(20)に向かって延在するスナッバ(26)と、
前記スナッバ(26)内に位置し下方の根元部スロット(28)へと延在しているスナッバ冷却システム(16)と、
低圧冷却空気を前記翼冷却システム(10)へと供給するために、低圧空気源(30)に流体連通しておりかつ前記概して細長い中空翼(32)内の前記翼冷却システム(10)の低圧サブシステム(7)に連通している低圧空気冷却システム(18)と、
高圧冷却空気を前記スナッバ冷却システム(16)に供給するために、高圧空気源(14)と、前記翼冷却システム(10)の前記スナッバ冷却システム(16)とに流体連通されている高圧冷却システム(24)であって、前記高圧冷却空気は、前記低圧冷却空気よりも高い圧力を有している、高圧冷却システム(24)と、
を備えるタービン翼(20)。 - 前記低圧空気冷却システム(18)は、周囲空気を前記翼冷却システム(10)へと供給するために、周囲空気源(30)に流体連通しておりかつ前記概して細長い中空翼(32)内の前記翼冷却システム(10)に連通している周囲空気冷却システム(18)である、請求項1記載のタービン翼(20)。
- 前記高圧冷却システム(24)は、圧縮機抽気を前記スナッバ冷却システム(16)に供給するために、圧縮機(14)と前記スナッバ冷却システム(16)とに流体連通された圧縮機抽気冷却システム(24)である、請求項1記載のタービン翼(20)。
- 前記圧縮機抽気冷却システム(24)に流体連通している前記圧縮機(14)は、前記タービン翼(20)が取り付けられているガスタービンエンジン(12)のタービン(54)に圧縮機抽気を供給する、請求項3記載のタービン翼(20)。
- 前記概して細長い翼(32)の前記根元部(44)の半径方向内側に位置する下方の根元部スロット(28)と、前記概して細長い翼(32)の前記根元部(44)の半径方向内側に位置する圧縮機空気マニホルド(60)と、をさらに備え、前記圧縮機空気マニホルド(60)は、前記下方の根元部スロット(28)の半径方向内側でディスク(80)内に位置している、請求項1記載のタービン翼(20)。
- 少なくとも1つの可動の空気供給管(62)をさらに備え、該空気供給管は、前記圧縮機空気マニホルド(60)における入口(64)と、前記概して細長い翼(32)内の通路(68)との係合と、該通路(68)との非係合との間で可動な出口(66)であって、前記下方の根元部スロット(28)内に位置している出口(66)と、を有している、請求項5記載のタービン翼(20)。
- 前記少なくとも1つの可動の空気供給管(62)はさらに、前記少なくとも1つの可動の空気供給管(62)が圧縮機抽気を含んでいる場合に、前記圧縮機空気マニホルド(60)に対して前記少なくとも1つの可動の空気供給管(62)をシールするために、前記圧縮機空気マニホルド(60)を形成する内壁(70)に適合するようになっている、前記入口(64)に隣接して位置するカラー(74)を有している、請求項6記載のタービン翼(20)。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/200,168 US9797259B2 (en) | 2014-03-07 | 2014-03-07 | Turbine airfoil cooling system with cooling systems using high and low pressure cooling fluids |
US14/200,168 | 2014-03-07 | ||
PCT/US2015/019350 WO2015134959A2 (en) | 2014-03-07 | 2015-03-09 | Turbine airfoil cooling system with cooling systems using high and low pressure cooling fluids |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2017518452A JP2017518452A (ja) | 2017-07-06 |
JP6231223B2 true JP6231223B2 (ja) | 2017-11-15 |
Family
ID=52682962
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2016555992A Expired - Fee Related JP6231223B2 (ja) | 2014-03-07 | 2015-03-09 | 高圧及び低圧の冷却流体を用いる冷却システムを備えたタービン翼 |
Country Status (5)
Country | Link |
---|---|
US (1) | US9797259B2 (ja) |
EP (1) | EP3114323A2 (ja) |
JP (1) | JP6231223B2 (ja) |
CN (1) | CN106103900B (ja) |
WO (1) | WO2015134959A2 (ja) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10227896B2 (en) * | 2016-03-17 | 2019-03-12 | Rolls-Royce Corporation | Flow segregator for infrared exhaust suppressor |
FR3072414B1 (fr) * | 2017-10-16 | 2019-11-01 | Safran Aircraft Engines | Dispositif et procede de refroidissement d'une turbine basse pression dans une turbomachine |
FR3073007B1 (fr) * | 2017-10-27 | 2019-09-27 | Safran Aircraft Engines | Dispositif de maintien d'un tube de refroidissement pour carter de turbomachine |
WO2020023005A1 (en) * | 2018-07-23 | 2020-01-30 | Siemens Aktiengesellschaft | Cover plate with flow inducer and method for cooling turbine blades |
Family Cites Families (31)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2931623A (en) | 1957-05-02 | 1960-04-05 | Orenda Engines Ltd | Gas turbine rotor assembly |
DE3069854D1 (en) | 1980-03-13 | 1985-02-07 | Bbc Brown Boveri & Cie | Vibration damper for turbine blades |
US5498126A (en) | 1994-04-28 | 1996-03-12 | United Technologies Corporation | Airfoil with dual source cooling |
JP3442959B2 (ja) | 1997-02-21 | 2003-09-02 | 三菱重工業株式会社 | ガスタービン動翼の冷却媒体通路 |
DE69823744T2 (de) * | 1997-07-07 | 2005-04-28 | Mitsubishi Heavy Industries, Ltd. | Anordnung von Gasturbinenlaufschaufeln mit einem Dampfkühlungssystem |
US5993150A (en) | 1998-01-16 | 1999-11-30 | General Electric Company | Dual cooled shroud |
US6389793B1 (en) * | 2000-04-19 | 2002-05-21 | General Electric Company | Combustion turbine cooling media supply system and related method |
US6487863B1 (en) | 2001-03-30 | 2002-12-03 | Siemens Westinghouse Power Corporation | Method and apparatus for cooling high temperature components in a gas turbine |
US6968696B2 (en) | 2003-09-04 | 2005-11-29 | Siemens Westinghouse Power Corporation | Part load blade tip clearance control |
US6960060B2 (en) | 2003-11-20 | 2005-11-01 | General Electric Company | Dual coolant turbine blade |
US7007488B2 (en) | 2004-07-06 | 2006-03-07 | General Electric Company | Modulated flow turbine nozzle |
US7189056B2 (en) | 2005-05-31 | 2007-03-13 | Pratt & Whitney Canada Corp. | Blade and disk radial pre-swirlers |
US7270517B2 (en) | 2005-10-06 | 2007-09-18 | Siemens Power Generation, Inc. | Turbine blade with vibration damper |
US7293953B2 (en) | 2005-11-15 | 2007-11-13 | General Electric Company | Integrated turbine sealing air and active clearance control system and method |
US7513738B2 (en) | 2006-02-15 | 2009-04-07 | General Electric Company | Methods and apparatus for cooling gas turbine rotor blades |
US7677048B1 (en) * | 2006-05-24 | 2010-03-16 | Florida Turbine Technologies, Inc. | Turbine last stage blade with forced vortex driven cooling air |
CN100370113C (zh) | 2006-07-06 | 2008-02-20 | 东方电气集团东方汽轮机有限公司 | 汽轮机动叶片围带结构 |
US7870743B2 (en) | 2006-11-10 | 2011-01-18 | General Electric Company | Compound nozzle cooled engine |
US7870742B2 (en) | 2006-11-10 | 2011-01-18 | General Electric Company | Interstage cooled turbine engine |
US7743613B2 (en) | 2006-11-10 | 2010-06-29 | General Electric Company | Compound turbine cooled engine |
US7926289B2 (en) * | 2006-11-10 | 2011-04-19 | General Electric Company | Dual interstage cooled engine |
US8079802B2 (en) | 2008-06-30 | 2011-12-20 | Mitsubishi Heavy Industries, Ltd. | Gas turbine |
US8157505B2 (en) | 2009-05-12 | 2012-04-17 | Siemens Energy, Inc. | Turbine blade with single tip rail with a mid-positioned deflector portion |
US8172507B2 (en) | 2009-05-12 | 2012-05-08 | Siemens Energy, Inc. | Gas turbine blade with double impingement cooled single suction side tip rail |
US8313287B2 (en) | 2009-06-17 | 2012-11-20 | Siemens Energy, Inc. | Turbine blade squealer tip rail with fence members |
US8616848B2 (en) | 2009-12-14 | 2013-12-31 | Siemens Energy, Inc. | Turbine blade damping device with controlled loading |
FR2954401B1 (fr) | 2009-12-23 | 2012-03-23 | Turbomeca | Procede de refroidissement de stators de turbines et systeme de refroidissement pour sa mise en oeuvre |
US8523525B2 (en) | 2010-02-05 | 2013-09-03 | Siemens Energy, Inc. | Snubber assembly for turbine blades |
US8684692B2 (en) | 2010-02-05 | 2014-04-01 | Siemens Energy, Inc. | Cooled snubber structure for turbine blades |
US20140056716A1 (en) | 2010-04-01 | 2014-02-27 | Stephen John Messmann | Bicast turbine engine components |
US9631500B2 (en) * | 2013-10-30 | 2017-04-25 | General Electric Company | Bucket assembly for use in a turbine engine |
-
2014
- 2014-03-07 US US14/200,168 patent/US9797259B2/en not_active Expired - Fee Related
-
2015
- 2015-03-09 EP EP15710086.8A patent/EP3114323A2/en not_active Withdrawn
- 2015-03-09 CN CN201580012400.7A patent/CN106103900B/zh not_active Expired - Fee Related
- 2015-03-09 WO PCT/US2015/019350 patent/WO2015134959A2/en active Application Filing
- 2015-03-09 JP JP2016555992A patent/JP6231223B2/ja not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
JP2017518452A (ja) | 2017-07-06 |
EP3114323A2 (en) | 2017-01-11 |
WO2015134959A2 (en) | 2015-09-11 |
US20150252688A1 (en) | 2015-09-10 |
CN106103900A (zh) | 2016-11-09 |
WO2015134959A3 (en) | 2015-11-05 |
CN106103900B (zh) | 2018-05-22 |
US9797259B2 (en) | 2017-10-24 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US20180328187A1 (en) | Turbine engine with an airfoil and insert | |
US8961108B2 (en) | Cooling system for a turbine vane | |
US10408066B2 (en) | Suction side turbine blade tip cooling | |
US9822662B2 (en) | Cooling system with compressor bleed and ambient air for gas turbine engine | |
JP6231223B2 (ja) | 高圧及び低圧の冷却流体を用いる冷却システムを備えたタービン翼 | |
US10830057B2 (en) | Airfoil with tip rail cooling | |
EP3190340A1 (en) | Cooled combustor for a gas turbine engine | |
US11208901B2 (en) | Trailing edge cooling for a turbine blade | |
US20170370232A1 (en) | Turbine airfoil cooling system with chordwise extending squealer tip cooling channel | |
JP2017141825A (ja) | ガスタービンエンジン用の翼形部 | |
US10830146B2 (en) | Compressor bleed cooling system for mid-frame torque discs downstream from a compressor assembly in a gas turbine engine | |
CN107084006B (zh) | 用于燃气涡轮发动机翼型件的加速器插入件 | |
US20170145835A1 (en) | Turbine airfoil cooling system with bifurcated mid-chord cooling chamber | |
US20180230812A1 (en) | Film hole arrangement for a turbine engine | |
CN108691658B (zh) | 具有平台冷却回路的涡轮发动机 | |
US20200102887A1 (en) | Gas turbine engine and cooling air configuration for turbine section thereof | |
US10626797B2 (en) | Turbine engine compressor with a cooling circuit | |
US20170081960A1 (en) | Turbine airfoil cooling system with platform cooling channels | |
WO2015191037A1 (en) | Turbine airfoil cooling system with leading edge diffusion film cooling holes |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20170718 |
|
A521 | Written amendment |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20170915 |
|
TRDD | Decision of grant or rejection written | ||
A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20171002 |
|
A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20171018 |
|
R150 | Certificate of patent or registration of utility model |
Ref document number: 6231223 Country of ref document: JP Free format text: JAPANESE INTERMEDIATE CODE: R150 |
|
LAPS | Cancellation because of no payment of annual fees |